固体发动机点火燃气流动与药柱变形耦合过程数值模拟(英文)  

Coupled numerical simulation for solid rocket motor ignition gas flow and propellant deformation

作　　者：曹琪[1] 李进贤[1] 唐金兰[1] 侯晓[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国航天科技集团公司第四研究院,西安710025

出　　处：《固体火箭技术》2010年第2期156-162,共7页Journal of Solid Rocket Technology

摘　　要：采用MpCC I耦合器作为FLUENT和ANSYS的数据交换平台,对带径向翼槽大长径比固体发动机点火过程中的流固耦合现象进行了数值模拟。结果表明,该型发动机点火瞬间燃气流动与药柱变形强烈耦合,药柱变形主要发生在径向翼槽台阶的尖点处,且随点火过程的推进变形加剧;中间翼槽尖点处药柱的变形量比头部翼槽处大,是造成发动机点火故障的主要原因。计算获得了点火压力冲击下药柱的位移及应力场的分布规律,文中的研究结果可为流固耦合技术在固体发动机上的应用奠定一定的基础。By using MpCCI coupler as the data exchange platform of FLUENT and ANSYS analysis software,the Fluid Structure Interaction（FSI） phenomenon during ignition process of large L/D ratio SRM with radial fin slot is simulated.The results show that ignition gas flow couples with grain deformation strongly at ignition transient of this type SRM,grain deformation occurs mainly at the cusp of radial fin slot step,which is aggravated along with ignition process.Grain deformation at the tip of middle fin slot is larger than the one of head fin slot,which results in ignition failure.The distribution of grain displacement and stress field is calculated under the impact of ignition pressure,and the research results can make certain groundwork for applying FSI technology to SRM.

关 键 词：固体发动机 点火瞬间 药柱变形 流固耦合 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]